EP0097490B1 - Distanz-/Seiten-/Höbenwinkel-Darstellung eines Schiffes zur Geschützsteuerung - Google Patents

Distanz-/Seiten-/Höbenwinkel-Darstellung eines Schiffes zur Geschützsteuerung Download PDF

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Publication number
EP0097490B1
EP0097490B1 EP83303482A EP83303482A EP0097490B1 EP 0097490 B1 EP0097490 B1 EP 0097490B1 EP 83303482 A EP83303482 A EP 83303482A EP 83303482 A EP83303482 A EP 83303482A EP 0097490 B1 EP0097490 B1 EP 0097490B1
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Prior art keywords
ship
radar
sight
range
velocity
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French (fr)
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EP0097490A3 (en
EP0097490A2 (de
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Sol Boles
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Grumman Corp
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Grumman Aerospace Corp
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
    • G01S13/66—Radar-tracking systems; Analogous systems
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
    • G01S13/88—Radar or analogous systems specially adapted for specific applications
    • G01S13/89—Radar or analogous systems specially adapted for specific applications for mapping or imaging
    • G01S13/90—Radar or analogous systems specially adapted for specific applications for mapping or imaging using synthetic aperture techniques, e.g. synthetic aperture radar [SAR] techniques
    • G01S13/904—SAR modes
    • G01S13/9092—SAR modes combined with monopulse techniques

Definitions

  • the present invention relates to radar controlled weapons systems and, more particularly, to a method and apparatus for generating real-time high resolution Synthetic Aperture Radar (SAR) imagery from an airborne platform of a translating ship under the influence of roll, pitch, and yaw motions characteristic of sea state conditions.
  • SAR Synthetic Aperture Radar
  • a highly resolved ship image on an airborne display permits targeting to a particular part of a ship for the purpose of standoff command guidance weapon delivery.
  • this invention relates to airborne SAR systems used for generating real-time high resolution imagery of a ship target under the influence of sea state conditions and for accurately measuring and tracking the range and azimuth angle of a designated resolution cell within the aforesaid displayed target area so as to enable the accurate delivery of an air-to-ground missile or glide bomb from the SAR bearing aircraft to the ship target.
  • the manner of weapon guidance depends upon reducing to zero the relative range and azimuth angle between weapon and designated target resolution cell.
  • the first invention provides an undistorted two-dimensional image of the ship from a direct plot of range versus interferometrically determined azimuth angle of all essential scatterers comprising the ship.
  • the second invention provides an improvement in image definition, as well as performance to greater ranges, by displaying range versus doppler, after removal of the isodop type distortions inherent in the formed range/doppler image.
  • each of the aforementioned inventions is subject to the limitations on image resolution brought about by the distributed elevation angles of the essential scatterers comprising the ship target.
  • US ⁇ A ⁇ 4 321, 601 discloses a SAR method and an apparatus involving motion compensation, range gating and doppler filtering as well interferometric measurements of the elevation angle associated with each range bin and each doppler cell.
  • an interferometer antenna comprising two elements spaced in elevation and the signals from these two elements are processed in separate channels, thereby enabling the measurement of the elevation angle from a comparison of the phases in the two channels on a cell by cell basis.
  • the prior art also provides centering and focusing functions.
  • the invention disclosed herein is related to the inventions described in the aforementioned copending European applications but by a unique processing implementation, is capable of removing any restrictions due to ship scatterer elevation on the formation of a scaled high resolution image. This advantage is brought about by utilizing elevation angle, as well as azimuth angle, interferometric techniques in conjunction with SAR signal processing techniques.
  • the object of the present invention may be generally described as providing a method and apparatus for forming, in conjunction with an airborne synthetic aperture radar system having an interferometer antenna and a display, high resolution synthetic aperture radar imagery of a ship target under the influence of sea state conditions.
  • the invention is defined in Claim 1.
  • a definition of the apparatus according to the invention is provided in Claim 9.
  • Aircraft and ship target geometrical and motional relationships which influence the doppler frequencies associated with the signals reflected from the ship target are illustrated in Figure 1.
  • the net doppler shift, f d associated with the signal reflected from a scatterer located at azimuth and elevation angle differences, and ⁇ , respectively, with respect to a boresight line-of-sight drawn to the center of ship rotation, considering for the moment, ship translation (without rotation), is given by where V xx , Vyy, and V zz represent the relative line-of-sight and cross line-of-sight velocity components due to both aircraft and ship translations, such that, and where the line-of-sight is drawn to the center of rotation of the ship.
  • Equation (5) can be stated, after motion compensation, Without further corrections, a doppler processed ship image would lack display centering in proportion to the error in line-of-sight velocity ⁇ v'xx . As noted in the aforementioned copending application, entitled “Range/doppler Ship Imaging For Ordnance Control", this error source could ordinarily be of considerable magnitude.
  • Equation (9) expresses doppler shift in terms of scatterer azimuth and elevation angles, and ⁇ , motion compensation velocity error ⁇ v'xx , and velocities V'yy and V' u , which themselves are functions of ship rotational velocities, W zz and Wyy, and suggests that the three velocity constants could be ascertained from the (over determined) set of measurement points, each one comprised of doppler, azimuth, and elevation angle measurements. To illustrate this, equation (9) is rearranged to read,
  • Doppler shift, f' d is related to doppler cell index, i l , after digital signal (Fourier Transform) processing, by where Np is the number of pulses integrated over the synthetic aperture, and f r is the pulse repetition frequency. From equations (10) and (11), It is to be noted that azimuth and elevation angles are determined interferometrically from azimuth and elevation phase shift measurements, ⁇ a and ⁇ e , where and d a and d e are azimuth and elevation interferometer baseline distances, respectively.
  • Equation (12) is of the form, where x, y and z denote doppler cell index, azimuth and elevation angles, respectively.
  • the three constants, a, b and c are solved for by performing a weighted least squares multivariate regression fit to the body of data, comprised of doppler, azimuth, and elevation angle coordinate values, using formulas from contemporary mathematical art.
  • estimates of the three constants, are expressed by, where, x i , y i , z i are the doppler cell index, azimuth, and elevation coordinates of the i th measurement point, and w i is a weighting factor proportional to the variance of each data point, determined by its signal to noise power ratio, a readily measurable quantity.
  • Requisite azimuth and elevation angle measurements for the performance of the regression solutions as depicted by Equations (16) through (19) are obtained by reference to Figure 2, which depicts the receiving aperture with four phase centers for azimuth and elevation signal separation.
  • Figure 2 depicts the receiving aperture with four phase centers for azimuth and elevation signal separation.
  • the sum of signals received at phase centers 2 and 3 are phase compared to the sum of signals received at phase centers 1 and 4 after coherent pulse integration and Fast Fourier Transform (FFT) digital signal processing, to yield in each and every range bin, the azimuth angle of similarly indexed doppler filters, in accordance with Equation (13).
  • phase comparison of the sum of signals received at 1 and 2 versus the sum of signals received at 3 and 4 yields elevation angle measurements in accordance with Equation (14), for similarly indexed doppler filters in. each range bin.
  • the regression solutions for v'xx , ' yy , and ' zz are used for the formation of the next synthetic aperture.
  • the determined error in system line-of-sight velocity v'xx permits a continual (aperture to aperture) update of the system V' xx estimate, thereby eliminating image azimuth centering errors by providing for an exact motion compensation correction for aircraft to ship net line-of-sight velocity.
  • the solutions for the net relative rotational velocities as denoted by V'yy and V' zz are used to establish doppler filter bandwidths and frequency separations, as well as the coherent integration time, for the formation of the next aperture of prescribed resolution.
  • W' zz and W'yy represent the net relative rotation rates between aircraft and ship derived from the regression solutions for V'yy and ' zz where and and there exists a net instantaneous axis of rotation, W' T , given by, Also, the doppler shift,
  • each synthetic aperture permits three scaled image projections with respect to the radar line-of-sight to be viewed on a cathode ray tube display, as illustrated in Figure 4, as an aid to ship identification. These are range/azimuth, elevation/azimuth, and range/elevation image projections.
  • elevation angle measurements apt to be less accurate than azimuth angle measurements because of antenna gain or interferometer baseline considerations. Accordingly, considerable benefit can be derived by way of elevation angle accuracy improvement for image display by utilizing the smoothed regression constants and the relatively accurate frequency and azimuth angle measurements. To see this, Equation (12) can be rewritten,
  • This elevation smoothing is another feature of the present invention and provides more accurate elevation/azimuth, and range/elevation image projections than would otherwise be obtained on the basis of the actual elevation angle measurements.
  • the present invention also has applicability to the technique for producing a range/doppler image of a ship under the influence of sea state conditions, developed by the U.S. Naval Research Laboratory and known as ISAR (Inverse Synthetic Aperture Radar) imaging.
  • ISAR Inverse Synthetic Aperture Radar
  • the name denotes the fact that SAR doppler resolution stems from predominant target rotation overthat arising from aircraft motion.
  • W' T an instantaneous net rotation vector, W' T , lying in the transverse plane to the radar line-of-sight, which determines the doppler frequency of any scatterer location projected onto the transverse plane, such as P', proportional to the distance h, of P' from the W' T axis, in accordance with Equation (26).
  • a range/doppler processed (ISAR) image is a representation of a projection along the W' T direction onto the projection plane, as depicted in Figure 5.
  • Such a projection provides profile information concerning the ship target in addition to subtended length along the slant range direction and is therefore useful for purposes of ship classification.
  • Chip profile is plotted vertically and slant range horizontally, so that ship elevation features plot more closely to the vertical direction on the CRT display). Since W' T is a constantly varying quantity both in magnitude and direction, with a strong dependence upon instantaneous ship rotational motions, observed ISAR imagery undergoes variations in elevation profile as well as image inversions as the sign of W'yy changes.
  • ISAR profile imaging has been useful as an aid to ship classification. It is inherently useful to relatively long range because adequate doppler imagery is achievable at modest signal to noise ratios. Due to the ever changing and unpredictable doppler history of any cursored range/doppler cell of the ship for targeting and weapon delivery purposes, however, sustained cursor tracking normally required during a weapon delivery phase is not achievable using ISAR.
  • the regression solution for the estimates of W'u and W', and hence the magnitude of the net rotational vector W' T provides the scaling along the doppler sensitive cross-range direction, as denoted by Equation (26). That is, in each range bin, the scaled cross-range displacement, h i , of each scatterer whose doppler shift is (Af),, is found from, and
  • Equations (30) and (31) provide for the removal of inversions in displayed imagery to facilitate ship recognition to the extent that such inversions depend upon the sign of W'ri.
  • the ISAR projection along the W' T direction can be converted to an equivalent "stretched” projection along the W'yy direction, which would have the further advantage of providing the maximum profile of the ship target as an aid to ship classification.
  • the "stretched" profile length, h',, associated with each scatterer, whose measured cross-range location is h i is found from, where, from equations (12) and (15), so that, or
  • the so-called “stretched” ISAR plot is displayed in the fourth quadrant of the split screen display depicted in Figure 4, and is virtually the same projection as the range/elevation image projection depicted directly above it.
  • the "stretched” projection provides useful quasi-profile imagery for values of ⁇ , (dependent upon relative net rotational vectors W'yy and W'a) between zero and about 60 degrees. For U between 60 and 90 degrees, the "stretched” ISAR image would suffer distortion, so that the scaled (unstretched) projection, more nearly representative of a plan (range/azimuth) projection, is most advantageously plotted.
  • the two approaches are used in complementary fashion; the three interferometrically derived range/azimuth, elevation/azimuth, and range/elevation plots provide 3 orthogonal ship image projections with no ship aspect angle sensitivity.
  • the "stretched" or “scaled” ISAR projections have aspect sensitivity, with a preference for bow to stern aspect, but provide useful imagery for ship classification to greater ranges due to inherent less noisiness in displayed imagery at the longer ranges.
  • Ship translational motion must be tracked so that antenna boresight and range swath start bear a constant relationship with respect to the ship.
  • Interferometric azimuth angle data from each useful ship resolution cell are averaged on an array-to-array basis.
  • the solution for aircraft to ship relative range rate is tracked so as to advance or retard the range swath start trigger in accordance with ship as well as aircraft motion, so that corresponding ship range increments correspond from pulse-to-pulse.
  • range rate and azimuth rate corrections are applied by the system computer so as to also steer antenna boresight in both azimuth and elevation in accordance with both ship and aircraft translational motions.
  • a high resolution range/azimuth ship image permits the placement of a cursor at the location within the image of a particular resolution cell constituting the designated target cell.
  • To carry out command weapon guidance to its ultimate accuracy capability requires that the cursor location be tracked through a succession of images so as to be continuously superimposed over the initially designated resolution cell since the weapon is targeted to the cursor location.
  • cursor tracking of a designated target cell is accomplished in terms of its predicted range/azimuth location reference to the SAR bearing aircraft on the basis of the derived relative translation between aircraft and ship from aperture to aperture, on the basis of the regression solution for line-of-sight velocity, denoted by v'xx .
  • the range and azimuth distance corrections dy and dx, respectively, to be applied to the cursor coordinate locations are, and where x and y are the initial cursor azimuth and range locations, and dt represents the time increment from initial cursor placement.
  • FIG. 7 a block diagram of the preferred embodiment of the system utilized for practicing the present invention is illustrated.
  • pulses of electromagnetic energy generated in a Coherent Transmitter 11 from reference signals derived in an Exciter/Frequency Synthesizer 12 are radiated from a Transmitting Antenna 9 so as to optimally illuminate a ship target under way on the surface of the sea.
  • Signals reflected from the ship target are received by an Interferometer Antenna 10 comprised of four separate receiving elements whose common boresight direction corresponds to that of the Transmitting Antenna 9.
  • Switching signals at the system pulse repetition frequency generated in a General Purpose Computer 17 are applied to an Azimuth And Elevation Array Switching Unit 8 for the purpose of combining signals received by the four antenna apertures so as to form interleaved azimuth and elevation signal pairs through two receiver channels (Receivers 13 and 14) for subsequent interferometric angle processing.
  • the signals from antenna arrays 1 and 2 are coherently added on a microwave hybrid summing network located in the Azimuth and Elevation Array Switching Unit 8, as are the signals from antenna Arrays 3 and 4, after which the two sums are separately inputted to the Receivers 13 and 14, respectively, representing inputs to two separate synthetic arrays for elevation interferometric phase comparison.
  • signals from antenna arrays 1 and 4 as well as arrays 2 and 3 are separately added and inputted to the Receivers 13 and 14, representing inputs to two separate synthetic arrays for azimuth interferometric phase comparison.
  • These analog signal components are digitzed in A/D Converters 15 and 16 at a sampling rate determined by system range resolution requirements.
  • These digitized samples are alternately sorted out on a pulse-to-pulse basis and are stored in a Bulk Memory 19 for the subsequent processing of 4 range/doppler matrices, two of which are requisite for elevation angle determination on a cell by cell basis, and two for azimuth.
  • motion compensation corrections for antenna phase center translational and rotational motions, as well as for ship translational motion are computed and stored in a Motion Compensation Unit 20 in a time sequenced order on the basis of computations performed in the General Purpose Computer 17 of the two-way line-of-sight displacement change between antenna phase centers and the tracking center-of- gravity of the ship, predicated on the regression solution obtained for the line-of-sight velocity error, e V l xx , performed in a Velocity Computer 27.
  • corrections stored in the Motion Compensation Unit 20 are applied to the time sequences stored in the Bulk Memory 19 in the form of vector rotations reflecting the two-way motion compensation phase correction to each range sample of each pulse of the four sequences stored in the Bulk Memory 19.
  • data is read out of the Bulk Memory 19 (as new data is being entered) for Fourier Transform digital signal processing to produce the necessary filtering so as to provide the desired resolution along the doppler sensitive direction and in each range bin in accordance with Equations 25 and 26, wherein the solutions for V'yy and V'zz are obtained from General Purpose Computer 17.
  • the filtering is performed in FFT Processors 21 to 24 which perform Fast Fourier Transform digital processing so as to produce doppler resolved coherently integrated vector sums in each filter of each range bin.
  • the processed outputs of FFT Processors 21 to 24 are seen to represent range/doppler resolved vectors representing, respectively, the net signal power in the upper (Arrays 1 and 2), lower (Arrays 3 and 4), left (Arrays 1 and 4) and right (Arrays 2 and 3) antenna sections throughout their respective sampled intervals.
  • Range/Azimuth Map Generator 26 which produces the interferometric spatial azimuth angle , associated with each resolved range/doppler cell, in accordance with where d a and ⁇ a are azimuth interferometer baseline length, and measured electrical phase of each resolution cell, respectively.
  • the range/doppler/elevation angle coordinates from the Range/Elevation Map Generator 25 and the range/doppler/azimuth angle coordinates form the Range/azimuth Map Generator 26 (for each range/ doppler resolved cell) are red into the Velocity Computer 27 where a weighted multivariate regression solution, using doppler, elevation, and azimuth angle variables, is performed for the regression constants, ⁇ , b and in accordance with Equations (16) to (19), from which the velocity constants, v'xx , V ' yy and ' zz , as specified by Equations (20) to (22), are computed in the General Purpose Computer 17.
  • the weight w, applied to each coordinate, x,, y, and z entering the regression solutions, are read into the Velocity Computer 27 from either of the FFT Processors 21-24 through either the Range/Elevation Map Generator 25 or the Range/Azimuth Map Generator 26.
  • the values of A, f r , and Np used in the evaluation of Equations (20) through (22) are operating constants available in General Purpose Computer 17, where f, represents the pulse repetition frequency governing the formation of the interleaved azimuth and elevation synthetic apertures, each of which occurs at one half the pulse repetition frequency at which pulses are transmitted.
  • the regression solution for v'xx in General Purpose Computer 17 serves as a correction of - v'xx to the line-of-sight velocity estimate.
  • Updated line-of-sight velocity is applied to the Motion Compensation Unit 20 which applies motion compensation phase corrections to data stored in the Bulk Memory 19 for the purpose of image focusing and to drive the residual doppler in the boresight direction, assumed centered at the center of rotation of the ship, to zero, so as to avoid possible doppler foldovers which could have a disturbing influence on the doppler/azimuth/elevation coordinate data provided to the Velocity Computer 27 for regression analysis.
  • the remaining two velocity estimates, V'yy and ' zz are used in General Purpose Computer 17 to compute doppler bandwidth, BW, and integration time, T, for the formation of the next aperture, in accordance with Equations (27) and (28), so as to achieve a prescribed resolution of d res along the doppler sensitive direction, where the slant range, R o in Equation (27) is known in the General Purpose Computer 17 on the basis of inputs from an Interial Navigation System 18.
  • the system pulse repetition frequency is twice f, due to manner in which the elevation and azimuth arrays are interleaved).
  • Azimuth and elevation angle data is scaled directly in feet along their respective directions in the Velocity Computer 27 by multiplying by slant range, R o , obtained from the General Purpose Computer 17.
  • Three sets of coordinate data depicting the locations of ship scatterers are transferred from the Velocity Computer 27 to a Scan Converter 28 for display on a split screen divided into four quadrants in a CRT Display 29. These are the range/azimuth, azimuth/elevation, and range/elevation coordinate values, representing the three orthogonal image projections of the ship target.
  • a representation of such image projections for a hypothetical ship target is shown in Figure 4.
  • interferometric angle measurements start to become noise because of angle glint errors accompanying such measurements arising from normal receiver thermal noise limitations for fixed transmitter and antenna parameters. Due to aperture restrictions governing elevation angle measurement accuracy in the system cited herein, elevation locational errors in displayed imagery at long range due to such expected measurement noise are substantially reduced.
  • the system range capability for displaying useful imagery can be materially extended by solving for smoothed elevation locational values on the basis of the equation governing the interrelationships of spacial angles, doppler frequency, and regression constants, stated by equation (29), as By substituting the values of regression constants, ⁇ , band , and the relatively accurate values of doppler cell index, i,, and azimuth angle, of each coordinate point into Equation 29, a smoothed value, ⁇ is obtained for each such coordinate point.
  • the smoothed elevation values, ⁇ , derived in this manner in the Velocity Computer 27, are read into the Scan Converter 28, to produce displayed images in the azimuth/elevation and range/elevation image projections of considerable greater accuracy than those that would have been produced by displaying the original elevation measurements themselves.
  • Antenna azimuth steering commands are generated in the General Purpose Computer 17 on the basis of aircraft navigational data inputs from the Inertial Navigation System 18 and averaged interferometric azimuth angle measurements from the various ship scatterers provided by the Range/Azimuth Map Generator 26, in such a manner as to maintain the average of all interferometric azimuth angles at zero (with respect to its electrical boresight) when smoothed with a tracking filter in the General Purpose Computer 17 over successive apertures.
  • the net pulse-to-pulse two-way line-of-sight displacement change due to relative translation motion between aircraft and ship computed in the General Purpose Computer 17 for purposes of motion compensation also serves as a basis for controlling the precise timing for the start of range sampling at the A/D Converters 15 and 16, so that corresponding samples from pulse-to-pulse over the coherent integration interval represent the same range increment of the ship.
  • the net-line-of-sight displacement change with time, in conjunction with aircraft altitude available in the General Purpose Computer 17 from other on-board sensors, is used to provide elevation steering to the transmitting and receiving Interferometer Antennas 9 and 10.
  • Cursor placement to a desired range/azimuth resolution cell of the ship image is achieved by operator designation of video signals through the General Purpose Computer 17 and applied to the Scan Converter 28. Cursor tracking of the designated ship target resolution cell during the weapon delivery phase is similarly controlled by the General Purpose Computer 17 on the basis of its computations of target cell range and azimuth angle change with time derived from its navigational solutions for translational motions between aircraft and ship, wherein said cursor video signals are injected into appropriate range/azimuth resolution cells as time progresses.
  • Second order corrections to cursor tracking of the designated ship target cell to eliminate potential tracking errors arising from ship rotational (yaw) motion are effected as previously described in the aforementioned co-pending application, entitled "Range/Azimuth Angle Ship Imaging For Ordnance Control".
  • the range/azimuth/elevation coordinates of the targeted part of the ship for standoff command guidance weapon delivery is indicated by the cursor location which is tracked in the General Purpose Computer 17.
  • Control signals for the pointing of the Antennae 9 and 10 and for pulse repetition frequency (prf) control of the coherent Transmitter 11 are obtained from the General Purpose Computer 17. All task management such as data transmission and initiation of subroutine sequences, are performed by a Radar Data Processor 30.
  • the useful range of the system can be extended by smoothing the derived velocities iv, V' yy and V, zz using state-of-the-art curve fitting techniques to such data derived over multiple apertures, implemented in the General Purpose Computer 17.

Claims (16)

1. Verfahren zur Erzeugung und Anzeige eines hochauflösenden Radarbildes von einem unter dem Einfluß von Seegang stehenden Schiffsziel mit Hilfe eines flugzeuggestützten Radarsystems mit synthetischer Apertur, das eine Interferometer-Antenne und eine Anzeigevorrichtung aufweist, mit folgenden Verfahrensschritten:
a) Regelung der Richtlinie der Justiereinrichtung der Interfetometer-Antenne derart, daß eine Radarbeleuchtung des Schiffsziels stattfindet,
b) zeitliche Steuerung der Entfernungsabtastung derart, daß korrespondierende, von Impuls zu Impuls gewonnene Abtastproben über das Integrationsintervall des Radarsystems gleichen Entfernungsinkrementen des Schiffsziels entsprechen,
c) Kompensieren von Phasenänderungen in den Signalen, die von den das Schiffsziel enthaltenden Streuern empfangen werden und sich aus den jeweiligen Bewegungen des das Radarsystem tragenden Flugzeugs und des Schiffs längs der Radarsichtlinie ergeben, unter Verwendung eines Schätzwertes der die reine Doppleverschiebung bewirkenden Geschwindigkeit des das Radarsystem tragenden Flugzeugs relativ zu dem Schiff,
d) interferometrisches Messen der Azimuthwinkel und der Elevationswinkel des in jedem der Dopplerfilter in jedem Entfernungsfach empfangenen und kompensierten Signals unter Verwendung der Signale, die von zwei Paaren von in Azimuth- bzw. Elevationsrichtung voneinander beabstandeten Antennenelementen empfangen werden, wobei die von jedem Paar von Antennenelementen empfangenen Signale einer Entfernungsabtastung und einer Dopplerfilterung unterzogen werden, so daß man für jedes Paar von Antennenelementen eine Bildinformation als Funktion der Entfernung und des Azimuths erhält, und wobei die interferometrische Messung in einem Phasenvergleich der jedem Paar von Antennenelementen zugeordneten Bildinformation besteht, gekennzeichnet durch folgende weitere Verfahrensschritte:
e) Gewinnen von Schätzwerten
(1) Des Fehlers der geschätzten, die reine Dopplerverschiebung bewirkenden Geschwindigkeit des das Radarsystem tragenden Flugszeugs relativ zu dem Schiff in Richtung der Sichtlinie,
(2) der die reine Dopplerverschiebung bewirkenden Geschwindigkeit des das Radarsystem tragenden Flugzeugs relativ zu dem Schiff quer zur Sichtlinie sowie.
(3) der die reine Dopplerschiebung bewirkenden Geschwindigkeit in der Richtung, die sowohl zur Relativgeschwindigkeit quer zur Sichtlinie und als auch zur Radarsichtlinie zum Rotationszentrum des Zielverfolgungspunktes des Schiffes orthogonal verläuft, aus ausgewählten Regressionskonstanten, die von einer auf die doppler-behandelten Azimuth- und Elevationswinkelmeßdaten angewendeten mehrdimensionalen Regression mit gewichteten kleinsten Quadraten abgeleitet sind,
f) Festlegen der Werte vorbestimmter Systemparameter, einschließlich der in dem nächstfolgenden Integrationsintervall bei der Erzeugung des hochauflösenden Bildes des Schiffsziels zu verwendenden Integrationszeit des Radar-systems mit synthetischer Apertur, der lmpulswiederholfrequenz, der Dopplerfilterbandbreite und der Abstände, aus der geschätzten Geschwindigkeit quer zur Sichtlinie und der geschätzten orthogonalen Geschwindigkeit,
g) Darstellen des erzeugten Bildes des Schiffsziels, einschließlich einer Entfernungs/ Azimuthwinkelprojektion, einer Azimuthwinkel/Elevationsprofilprojection und einer Entfernungs/ Elevationsprofilprojektion und
h) Zentrieren des dargestellten Bildes des Schiffsziels unter Verwendung des geschätzten Fehlers der geschätzten Relativgeschwindindigkeit in Richtung der Sichtlinie.
2. Verfahren nach Anspruch mit den weiteren Verfahrensschritten des
Markierens einer spezifizierten Auflösungszelle des dargestellten Bildes des Schiffsziels mittels Cursor und des
Nachführens der Entfernung und des interferometrischen Azimuthwinkels dieser spezifizierten Auflösungszelle des Schiffsziels von Apertur zu Apertur.
3. Verfahren nach Anspruch 2, mit dem weiteren Verfahrensschritt, daß der Cursor auf einer Basis von Apertur zu Apertur einer Nachführkorrektur unterzogen wird, um die Rotation des Schiffs um die Achse zu kompensieren, die sowohl zur Relativegeschwindigkeit quer zur Sichtlinie und als auch zur Radarsichtlinie zum Rotationszentrum des Zielverfolgungspunktes des Schiffes orthogonal verläuft.
4. Verfahren nach einem der Ansprüche 1 bis 3, mit den weiteren Verfahrensschritten der Gewinnung und Verwendung von geglätteten Elevationsortswerten bei der Erzeugung der dargestellten Azimuthwinkel/Elevationsprofil- und Entfernungs/Elevationsprofil-Bildprojektion des Schiffsziels.
5. Verfahren nach einem der Ansprüche 1 bis 4, mit folgenden weiteren Verfahrensschritten:
a) Glätten der Schätzwerte
(1) des Fehlers der geschätzten, die reine Dopplerverschiebung bewirkenden Geschwindigkeit des das Radarsystem tragenden Flugszeugs relativ zu dem Schiff in Richtung der Sichtlinie,
(2) der die reine Dopplerverschiebung bewirkenden Geschwindigkeit des das Radarsystem tragenden Flugzeugs relativ zu dem Schiff quer zur Sichtlinie sowie
(3) der die reine Dopplerverschiebung bewirkenden Geschwindigkeit in der Richtung, die sowohl zur Relativgeschwindigkeit quer zur Sichtlinie und als auch zur Radarsichtlinie zum Rotationszentrum des Zielverfolgungspunktes des Schiffes ortghogonal verläuft, unter Verwendung der über mehrere Aperturen gewonnenen, dopplerbehandelten Meßdaten der Azimuth-und Elevationswinkel,
b) Festlegen der vorbestimmten, in dem nächstfolgenden Integrationsintervall bei der Erzeugung des hochauflösenden Bildes des Schiffsziels prädiktiv zu verwendenden Systemparameter aus dem geglätteten Schätzwert der Relativgeschwindigkeit quer und dem geglätteten Schätzwert der orthogonalen Geschwindigkeit
c) Darstellen des erzeugten Bild des Schiffsziels und
d) Zentrieren des dargestellten Bildes des Schiffsziels unter Verwendung des geschätzten Fehlers der geschätzten Relativgeschwindigkeit in Richtung der Sichtlinie.
6. Verfahren nach einem der vorhergehenden Ansprüche mit dem weiteren Verfahrensschritten des Erzeugens und Darstellens einer inversen Profilbildprojektion des Schiffsziels durch das Radarsystem mit synthetischer Apertur.
7. Verfahren nach Anspruch 6 mit dem weiteren Verfahrensschritt der Skalierung der Quer-Entfernungsdimension der dargestellten inversen Profilbildprojektion des Schiffsziels.
8. Verfahren nach Anspruch 7 mit dem weiteren Verfahrensschritt des Umwandels der dargestellten, skalierten inversen Profilbildprojektion des Schiffsziels in eine gespreizte inverse Profilbildprojektion.
9. Flugzeuggestütztes Radarsystem mit synthetischer Apertur zur Erzeugung und Darstellung eines hochauflösenden Radarbildes eines unter dem Einfluß von Seegang stehenden Schiffsziels
mit einer Interferometer-Antenne (10) mit mehreren Sektionen, die wirkungsmäßig mit dem Eingang eines Zweikanalempfängers und einem Doppler-Verarbeitungssystem (13-16, 19, 21-24) verbunden ist,
mit einer Anzeigevorrichtung (29), die wirkungsmaßig mit dem Ausgang des Zweikanalempfängers und dem Doppler-Verarbeitungssystem verbunden ist,
sowie mit einer Bildsignalverarbeitungseinrichtung (17, 20, 25-28), die folgende Teile umfaßt:
a) Mittel (17) zur Regelung der Richtlinie der Justiereinrichtung der Interferometer-Antenne derart, daß eine Radarbeleuchtung des Schiffsziels erfolgt,
b) Mittel (17) zur zeitlichen Steuerung der Entfernungsabtastung derart, daß korrespondierende, von Impuls zu Impuls gewonnene Abtastproben über das Integrationsintervall des Radarsystems gleichen Entfernungsinkrementen des Schiffsziels entsprechen,
c) Mittel (20) zum Kompensieren von Phasenänderungen in den Signalen, die von den das Schiffsziel enthaltenden Streuern empfangen werden und sich aus den jeweiligen Bewegungen des das Radarsystem tragenden Flugzeugs und des Schiffs längs der Radarsichtlinie ergeben, unter Verwendung eines Schätzwertes der die reine Dopplerverschiebung bewirkenden Geschwindigkeit des das Radarsystem tragenden Flugzeugs relativ zu dem Schiff, sowie
d) Mittel (25, 26) zum interferometrischen Messen der Azimuthwinkel und der Elevationswinkel des in jedem der Dopplerfilter in jedem Entfernungsfach empfangenen und kompensierten Signals unter Verwendung der Signale, die von zwei Paaren von in Azimuth- bzw. Elevationsrichtung voneinander beabstandeten Antennenelementen empfangen werden, wobei die von jedem Paar von Antennenelementen empfangenen Signale einer Entfernungsabtastung und einer Dopplerfilterung unterzogen werden, so daß man für jedes Paar von Antennenelementen eine Bildinformation als Funktion der Entfernung und des Azimuths erhält, und wobei die interferometrische Messung in einem Phasenvergleich der jedem Paar von Antennenelementen zugeordneten Bildinformation besteht, dadurch gekennzeichnet, daß die Bildsignalverarbeitungseinrichtung ferner folgende Teile umfaßt:
e) Mitel (17, 21) zum Gewinnen von Schätzwerten
(1) des Fehlers der geschätzten, die reine Dopplerverschiebung bewirkenden Geschwindigkeit des das Radarsystem tragenden Flugszeugs relativ zu dem Schiff in Richtung der Sichtlinie,
(2) der die reine Dopplerverschiebung bewirkenden Geschwindigkeit des das Radarsystem tragenden Flugszeugs relativ zu dem Schiff quer zur Sichtlinie sowie
(3) der die reine Dopplerverschiebung bewirkenden Geschwindigkeit in der Richtung, die sowohl zur Relativgeschwindigkeit quer zur Sichtlinie und als auch zur Radarsichtlinie zum Rotationszentrum des Zielverfolgungspunktes des Schiffes orthogonal verläuft, aus ausgewählten Regressionskonstanten, die von einer auf die doppler-behandelten Azimuth- und Elevationswinkelmeßdaten angewendeten mehrdimensionalen Regression mit gewichteten kleinsten Quadraten abgeleitet sind,
f) Mittel (17) zum Festlegen der Werte vorbestimmter Systemparameter, einschließlich der in dem nächstfolgenden Integrationsintervall bei der Erzeugung des hochauflösenden Bildes des Schiffsziels zu verwendenden Integrationszeit des Radarsystems mit synthetischer Apertur, der Impulswiederholfrequenz, der Dopplerfilterbandbreite und der Abstände, aus der geschätzten Geschwindigkeit quer zur Sichtlinie und der geschätzten orthogonalen Geschwindigkeit,
g) Mittel (28) zum Darstellen des erzeugten Bildes des Schiffsziels, einschließlich einer Entfernungs-/ Azimuthwinkelprojektion, einer Azimuthwinkel/Elevationsprofilprojektion und einer Entfernungs-/ Elevationsprofilprojektion auf der Anzeigevorrichtung sowie
h) Mittel (17) zum Zentrieren des dargestellten Bildes des Schiffsziels unter Verwendung des geschätzten Fehlers der geschätzten Relativgeschwindigkeit in Richtung der Sichtlinie.
10. Radarsystem nach Anspruch 9, bei dem die Bildsignalverarbeitungseinrichtung ferner Mittel (17) umfaßt, zum Markieren einer spezifizierten Auflösungszelle des dargestellten Bildes des Schiffsziels mittels Cursor und zum Nachführen der Entfernung und des interferometrischen Azimuthwinkels dieser spezifizierten Auflösungszelle des Schiffsziels von Apertur zu Apertur.
11. Radarsystem nach Anspruch 10, bei dem die Bildsignalverarbeitungseinrichtung ferner Mittel (17) umfaßt, die bewirken, daß der Cursor auf einer Basis von Apertur zu Apertur eines Nachführkorrektur unterzogen wird, um die Rotation des Schiffs um die Achse zu kompensieren, die sowohl zur Relativgeschwindigkeit quer zur Sichtlinie und als auch zur Radarsichtlinie zum Rotationszentrum des Zielverfolgungspunktes des Schiffes orthogonal verläuft.
12. Radarsystem nach einem der Ansprüche 9 bis 11, bei dem die Bildsignalverarbeitungseinrichtung ferner Mittel (17) umfaßt zur Gewinnung und Verwendung von geglätteten Elevationsortswerten bei der Erzeugung der dargestellten Azimuthwinkel/Elevationsprofil- und Entfernungs/Elevationsprofil-Bildprojektion des Schiffsziels.
13. Radarsystem nach einem der Ansprüche 9 bis 12, bei dem Bildsignalverarbeitungseinrichtung ferner folgende Teil umfaßt:
a) Mittel (17) zum Glätten der Schätzwerte für
(1) den Fehler in der geschätzten, die reine Dopplerverschiebung bewirkenden Geschwindigkeit des das Radarsystem tragenden Flugzeugs relativ zu dem Schiff in Richtung der Sichtlinie,
(2) die die reine Doppierverschiebung bewirkende Geschwindigkeit des das Radarsystem tragenden Flugzeugs relativ zu dem Schiff quer zur Sichtlinie sowie
(3) die die reine Dopplerverschiebung bewirkende Geschwindigkeit in der Richtung, die sowohl zur Relativgeschwindigkeit quer zur Sichtlinie und als auch zur Radarsichtlinie zum Rotationszentrum des Zielverfolgungspunktes des Schiffes orthogonal verläuft, unter Verwendung der über mehrere Aperturen gewonnenen, dopplerbehandelten Meßdaten der Azimuth-und Elevationswinkel,
b) Mittel (17) zum Festlegen der vorbestimmten Systemparameter, die in dem nächstfolgenden Integrationsintervall bei der Erzeugung des hochauflösenden Bildes des Schiffsziels prädiktiv zu verwendend sind, aus dem geglätteten Schätzwert der Relativgeschwindigkeit quer und dem geglätteten Schätzwert der orthogonalen Geschwindigkeit
c) Mittel (28) zum Darstellen des erzeugten Bild des Schiffsziels und
d) Mittel (17) zum Zentrieren des dargestellten Bildes des Schiffsziels unter Verwendung des geschätzten Fehlers der geschätzten Relativgeschwindigkeit in Richtung der Sichtlinie.
14. Radarsystem nach einem der Ansprüche 9 bis 13, bei dem die Bildsignalverarbeitungseinrichtung ferner Mittel (17) umfaßt zum Erzeugen und Darstellen einer inversen Profilbildprojektion des Schiffsziels durch das Radarsystem mit synthetischer Apertur.
15. Radarsystem nach Anspruch 14, bei dem die Bildsignalverarbeitungseinrichtung ferner Mittel (17) umfaßt zur Skalierung der Quer-Entfernungsdimension der dargestellten inversen Profilbildprojektion des Schiffsziels.
16. Radarsystem nach Anspruch 15, bei dem die Bildsignalverarbeitungseinrichtung ferner Mittel (17) umfaßt zum Umwandeln der dargestellten, skalierten inversen Profilbildprojektion des Schiffsziels in eine gespreizte inverse Profilbildprojektion.
EP83303482A 1982-06-17 1983-06-16 Distanz-/Seiten-/Höbenwinkel-Darstellung eines Schiffes zur Geschützsteuerung Expired EP0097490B1 (de)

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